Gas turbine engine component having variable width feather seal slot

Patent metadata

Field	Value
Publication number	US-2016003079-A1
Application number	US-201414769210-A
Country	US
Kind code	A1
Filing date	Mar 6, 2014
Priority date	Mar 8, 2013
Publication date	Jan 7, 2016
Grant date	—

Abstract

A component for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a mate face and a feather seal slot axially extending along the mate face, the feather seal slot having a variable width along a portion of its axial length.

First claim

What is claimed is:

1 . A component for a gas turbine engine, comprising:
a mate face; and a feather seal slot axially extending along said mate face, said feather seal slot having a variable width along a portion of its axial length.

2 . The component as recited in claim 1 , wherein said component is a vane.

3 . The component as recited in claim 2 , wherein said vane is a turbine vane.

4 . The component as recited in claim 1 , wherein said mate face is part of a platform.

5 . The component as recited in claim 1 , wherein said component is part of a blade outer air seal (BOAS).

6 . The component as recited in claim 1 , wherein said feather seal slot includes a first axial slot portion of a first width and a second axial slot portion of a second width that is different from said first width.

7 . The component as recited in claim 6 , wherein said second width is smaller than said first width.

8 . The component as recited in claim 1 , wherein said feather seal slot includes a first axial slot portion, a second axial slot portion and a radial slot portion between said first axial slot portion and said second axial slot portion.

9 . The component as recited in claim 8 , wherein said first axial slot portion extends upstream of said radial slot portion and said second axial slot portion extends downstream of said radial slot portion.

10 . The component as recited in claim 1 , comprising a feather seal received within said feather seal slot.

11 . The component as recited in claim 1 , comprising a first feather seal and a second feather seal received within said feather seal slot.

12 . The component as recited in claim 11 , wherein said first feather seal extends within a first axial slot portion and a second axial slot portion of said feather seal slot and said second feather seal extends within said first axial slot portion but not within said second axial slot portion.

13 . A gas turbine engine, comprising:
a first component having a first mate face; a second component having a second mate face circumferentially adjacent to said first mate face of said first component, wherein at least one of said first mate face and said second mate face include a feather seal slot having a first axial slot portion of a first width and a second axial slot portion of a second width that is different from said first width; and at least one feather seal received within said feather seal slot.

14 . The gas turbine engine as recited in claim 13 , wherein said at least one feather seal includes a first feather seal and a second feather seal.

15 . The gas turbine engine as recited in claim 14 , wherein a bent portion of said second feather seal extends into a radial slot portion of said feather seal slot.

16 . The gas turbine engine as recited in claim 13 , wherein a radial slot portion intersects said feather seal slot between said first axial slot portion and said second axial slot portion.

17 . A method of sealing between adjacent components of a gas turbine engine, comprising the steps of:
forming a feather seal slot having a variable width in a mate face of a component; and positioning at least one feather seal within the feather seal slot.

18 . The method as recited in claim 17 , wherein the step of forming includes forming the feather seal slot to include a first axial slot portion of a first width and a second axial slot portion of a second width that smaller than the first width.

19 . The method as recited in claim 18 , wherein the step of forming includes intersecting between the first axial slot portion and the second axial slot portion with a radial slot portion of the feather seal slot.

20 . The method as recited in claim 17 , wherein the step of positioning includes:
loading a first feather seal into a first axial slot portion and a second axial slot portion of the feather seal slot; and loading a second feather seal into the first axial slot portion but not the second axial slot portion.

Assignees

• United Technologies Corp

Inventors

• Boeke Mark A
• Rajchel Kevin
• Salzillo Richard M
• Degray Jeffrey J
• Mainelli Allison

Classifications

• F05D2240/11

  Shroud seal segments · CPC title

• F05D2240/57

  Leaf seals · CPC title

• F01D11/005 Primary

  Sealing means between non relatively rotating elements · CPC title

• F01D9/041

  using blades (F01D5/148 takes precedence) · CPC title